CN111746820B - Aircraft engine flight test system and test method - Google Patents
Aircraft engine flight test system and test method Download PDFInfo
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- CN111746820B CN111746820B CN201910241341.0A CN201910241341A CN111746820B CN 111746820 B CN111746820 B CN 111746820B CN 201910241341 A CN201910241341 A CN 201910241341A CN 111746820 B CN111746820 B CN 111746820B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention relates to an aircraft engine flight test system and a test method, wherein the test system comprises an unmanned flight test platform (1), and the unmanned flight test platform (1) comprises: the device comprises a machine body (11), wherein a mounting component is arranged at the outer bottom of the machine body (11) and used for mounting a test engine (14); and an operating engine (12) provided at a side of the body (11). On the basis of meeting the requirement of a test task, the test system has small redundancy in functions, structures and weights, low test cost and high economy; moreover, the test engine is additionally installed, so that the original running engine is not influenced, and the original structure of the unmanned flight test platform is not required to be modified; in addition, the test engine fails to work normally, the original running engine can still meet the flight requirement, and no test personnel need to be involved on the test platform provided with the test engine, so that the safety in the test process can be ensured.
Description
Technical Field
The invention relates to the technical field of aero-engine tests, in particular to an aero-engine flight test system and a test method.
Background
The aeroengine needs to carry out an aeroengine high-altitude test to determine the air operation characteristic in the design, the design and the airworthiness evidence obtaining, and the national GJB241A-2010 general Specification for aeroturbine jet engines and turbofan engines clearly stipulates that the high-altitude test is to be carried out on a high-altitude platform or a flight platform.
In the development of foreign civil aviation engines, the flight platform is an indispensable development means, and each main engine manufacturer has a flight test platform. Based on the consideration of cost, operation safety and engine size, the conventional large engine is usually developed into an aerial test by adopting a general flight test platform and is generally formed by modifying a general passenger plane or a transport plane, and a certain operating engine on the flight test platform is dismantled and replaced into a test engine in the test. Based on the consideration of safety, the flight test platform is usually modified on 4 or more airplanes (more than two airplanes), but in the actual test process, the cost required by airplane modification and the engine test cost are high, the running economy is poor, and the personnel safety risk exists for the participants because the tested engines are not standardized and proved.
Disclosure of Invention
The embodiment of the invention provides a flight test system and a flight test method for an aero-engine, which can reduce the test cost of the aero-engine.
According to an aspect of the invention, an aircraft engine flight test system is provided, comprising an unmanned flight test platform, wherein the unmanned flight test platform comprises:
the device comprises a machine body, wherein the outer bottom of the machine body is provided with a mounting component for mounting a test engine; and
the running engine is arranged at the side part of the machine body.
In some embodiments, the mounting member is provided at a middle region of the fuselage in the lateral direction, and is configured to mount the test engine in the longitudinal direction at a centerline of the fuselage.
In some embodiments, the mounting member includes a hanger structure for attachment to the top of the test engine.
In some embodiments, there are two operating engines, each located under a wing on either side of the fuselage.
In some embodiments, the test system further comprises a flying companion aircraft, wherein the flying companion aircraft is a manned aircraft and is used for flying with the unmanned flight test platform, monitoring the test state of the unmanned flight test platform in the air and/or controlling the operation of the unmanned flight test platform.
In some embodiments, the testing system further comprises a ground control station for monitoring the test status of the unmanned aerial vehicle test platform on the ground and/or controlling the operation of the unmanned aerial vehicle test platform.
In some embodiments, the test system further comprises a flying companion aircraft and a ground control station, wherein the flying companion aircraft and the ground control station independently control the operation of the unmanned aerial vehicle test platform, and the flying companion aircraft or the ground control station independently control the operation of the unmanned aerial vehicle test platform at the same time.
In some embodiments, when the preset test airspace is not more than the preset distance from the ground control station, the ground control station controls the operation of the unmanned flight test platform in a normal state, and the accompanying flight aircraft takes over the control of the operation of the unmanned flight test platform in an emergency; and/or
When the distance between the preset test airspace and the ground control station exceeds the preset distance, the accompanying flying aircraft controls the operation of the unmanned flying test platform.
In some embodiments, the test system further comprises a companion aircraft and a ground control station, wherein,
the accompanying airplane and the unmanned flight test platform, the accompanying airplane and the ground control station and the unmanned flight test platform and the ground control station are communicated through data chains;
the unmanned flight test platform is used for directly transmitting the operation state data to the ground control station and/or transmitting the operation state data to the ground control station through the backup and relay of the accompanying flying aircraft.
In some embodiments, the unmanned flight test platform includes a flight control system including a thrust control module for adjusting a thrust of the operating engine to meet a test thrust requirement of the test engine.
According to another aspect of the invention, a testing method of the aircraft engine flight testing system based on the embodiment is provided, and the testing method comprises the following steps:
enabling the unmanned flight test platform to be in a preset test airspace;
controlling the unmanned flight test platform to operate to execute a preset test project; and
and returning the unmanned flight test platform to the running state data.
In some embodiments, the assay method further comprises:
the test state of the unmanned flight test platform is monitored in the air by flying with the unmanned flight test platform; and/or
And monitoring the test state of the unmanned flight test platform on the ground through a ground control station.
In some embodiments, the step of controlling the operation of the unmanned aerial vehicle test platform specifically includes:
the operation of the unmanned flight test platform is independently controlled by the accompanying flying aircraft; or
The operation of the unmanned flight test platform is independently controlled through a ground control station.
In some embodiments, the test system includes a companion aircraft and a ground control station, and the step of controlling the operation of the unmanned aerial vehicle test platform specifically includes:
judging whether a preset test airspace exceeds a preset distance from a ground control station, if not, controlling the operation of the unmanned flight test platform through the ground control station in a normal state, and taking over the unmanned flight test platform through an accompanying flying aircraft in an emergency; and if the number exceeds the preset value, controlling the operation of the unmanned flight test platform through the accompanying flight plane.
In some embodiments, the test system includes a companion aircraft and a ground control station, and the step of returning the unmanned aerial vehicle test platform to the operating state data specifically includes:
the unmanned flight test platform directly transmits the running state data to the ground control station, or transmits the running state data to the ground control station through the backup of the accompanying flying aircraft and the relay.
In some embodiments, a flight control system is disposed in the unmanned flight test platform, the flight control system includes a thrust control module, and the step of controlling the operation of the unmanned flight test platform to execute the predetermined test item specifically includes:
the thrust of the operating engine is adjusted by the thrust control module to meet the test thrust requirements of the test engine.
In some embodiments, before the unmanned aerial vehicle is in the preset test airspace, the method further comprises:
and taking off the companion aircraft to wait for the unmanned flight test platform to take off in the air.
In some embodiments, before the unmanned aerial vehicle test platform is in the preset test airspace, the method further comprises:
and presetting a flight test program on the unmanned flight test platform so that the unmanned flight test platform automatically finishes a preset test project.
Based on the technical scheme, the aircraft engine flight test system provided by the embodiment of the invention adopts the unmanned flight test platform to carry out an air test on the aircraft engine, and the unmanned flight test platform has the advantages that compared with a passenger plane or a transport plane, the unmanned flight test platform is small in size, light in weight and small in number of running engines, so that on the basis of meeting the requirement of a test task, the redundancy in the aspects of functions, structures and weight is small, the test cost is low, and the aircraft engine flight test system has high economy; moreover, the test engine is additionally installed, so that the original running engine is not influenced, and the original structure of the unmanned flight test platform is not required to be modified; in addition, the test engine fails to work normally, the original running engine can still meet the flight requirement, and no test personnel need to be involved on the test platform provided with the test engine, so that the safety in the test process can be ensured.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a top view of one implementation of an unmanned flight test platform in an aircraft engine flight test system of the present invention;
FIG. 2 is a front view of one implementation of an unmanned flight test platform in the aircraft engine flight test system of the present invention;
FIG. 3 is a schematic block diagram of one implementation of an aircraft engine flight test system of the present invention.
Detailed Description
The present invention is described in detail below. In the following paragraphs, different aspects of the embodiments are defined in more detail. Aspects so defined may be combined with any other aspect or aspects unless clearly indicated to the contrary. In particular, any feature considered to be preferred or advantageous may be combined with one or more other features considered to be preferred or advantageous.
The terms "first", "second", and the like in the present invention are merely for convenience of description to distinguish different constituent elements having the same name, and do not denote a sequential or primary-secondary relationship.
The use of the terms "upper," "lower," "top," "bottom," "front," "back," "inner" and "outer" herein to describe an orientation or positional relationship is meant for convenience in describing the present invention and is not intended to imply or imply that the referenced devices must be in a particular orientation, constructed and operated in a particular orientation and therefore should not be considered limiting of the scope of the present invention.
The inventor discovers that the main reason that the conventional flight test platform adopts the test engine to replace the original engine is that the airplane body of the passenger plane or the transport plane is designed for carrying personnel or goods, the installation of the test engine cannot be increased below the airplane body due to the structural limitation, and the safe flight weight of the airplane can be exceeded due to the additional increase of the test engine. Therefore, the existing civil large turbofan engine is used for installing the test engine on the flight test platform through the switching hanger, so that the universality of the flight test platform is realized.
In addition, four airplanes or transporters are generally adopted for modification on the flight test platform, the main reason is that the test engines are not subjected to multiple flight tests, the safety performance of the test engines is difficult to guarantee, and when performance instability or failure occurs in the test process, thrust required by airplane flight can be maintained through other three engines, so that the flight safety is guaranteed. Moreover, the technology of the general-purpose aircraft is relatively mature, and the general-purpose aircraft is taken as a flight test platform at present from the viewpoint of pilot safety.
However, the inventors have noted that such flight test platforms still have some drawbacks, such as: the design goal of large multi-aircraft is generally to carry large numbers of people or cargo to perform long-range flights. For engine flight testing, it is common to perform flight testing tasks in limited airspace. In order to meet the requirements of passenger transport or transportation, large-scale airplanes are equipped with a passenger cabin or a cargo hold, and in an engine air test, the passenger cabin or the cargo hold is basically unloaded, the airplanes are in an unloaded state generally, and in certain flight subjects, the large-scale airplanes are even equipped with a counterweight system to simulate the normal operation state of the airplanes. Moreover, the operating conditions of the flight test platform are different from the typical operating conditions of large multi-engine aircrafts greatly, the load is low in flight, and a large amount of redundant structural weight is borne. Therefore, the flight test platform has high operation and maintenance cost and poor economy.
Moreover, the existing flight test platforms are all piloted, the test engine is not shaped and evidence is obtained, and the influence on the personal safety of the participants in the test is inevitable.
Therefore, through long-term research on the engine test process, the inventor finds that the flight test platforms obtained by modifying the existing large aircrafts have the problems of higher operation and maintenance cost, poor operation economy, higher modification and construction cost and personal safety risk of participants.
On the basis of finding the defects, the invention mainly improves the existing flight test platform from the viewpoint of improving the economy and the safety of the flight test, and aims to design a more efficient, concise and safe engine flight test system for the test flight work of a large civil aviation turbofan engine.
As shown in fig. 1 and 2, the present invention provides an aircraft engine flight test system, for example, for use in test flight work before large civil turbofan engine sizing, and in some embodiments, the test system includes an unmanned flight test platform 1, such as an unmanned aerial vehicle, which may use a large unmanned aerial vehicle driven by a turbofan or turboprop engine as a vehicle platform, or may also use other unmanned aerial vehicles capable of flying. The unmanned flight test platform 1 comprises a machine body 11, wherein a mounting component is arranged at the outer bottom of the machine body 11 and used for mounting a test engine 14; and the operation engine 12 is arranged on the side part of the fuselage 11, for example, the unmanned aerial vehicle flight test platform 1 can adopt a fixed wing unmanned aerial vehicle, the side part of the fuselage 11 is provided with a side wing 13, and the operation engine is hung at the bottom of the side wing 13.
The test system of the embodiment of the invention has at least one of the following advantages:
1. the unmanned aerial vehicle flight test platform is adopted to carry out aerial test on the aero-engine, and compared with a passenger plane or a transport plane, the unmanned aerial vehicle flight test platform is free of a passenger cabin or a cargo cabin, small in size, light in weight, small in number of running engines, and small in redundancy in functions, structure and weight on the basis of meeting the requirement of a test task, the structural complexity of the engine flight test platform is reduced, the design difficulty and test cost of the unmanned aerial vehicle flight test platform can be reduced, the running efficiency is improved, high economy is achieved, and conditions are provided for carrying out repeated tests before the aero-engine is shaped and evidence is obtained.
2. Through additionally installing the test engine on the unmanned flight test platform, the original operation engine is not influenced, the original structure of the unmanned flight test platform is not required to be modified, the test efficiency is high, and the test can be flexibly carried out on the aero-engine.
3. Although the number of the running engines in the unmanned flight test platform is small, the test engines are additionally arranged at the bottom of the aircraft body, and even if the test engines fail to work normally, the original running engines can still meet the flight requirements, so that the safety of the unmanned flight test platform in the test process is ensured.
4. Because the test engine is not shaped yet and has certain safety risk, the unmanned flight test platform is adopted for testing, and no test personnel need to be involved on the test platform provided with the test engine, so that the risk of injury to the personnel can be reduced in the test process.
As shown in fig. 1, the unmanned aerial vehicle flight test platform 1 is a fixed wing unmanned aerial vehicle, and includes a vehicle body 11, two side wings 13 and two tail wings 17, wherein the two side wings 13 are respectively disposed on the left and right sides of the front region of the vehicle body 11 along the longitudinal direction, and the two tail wings 17 are respectively disposed on the left and right sides of the rear region of the vehicle body 11 along the longitudinal direction. Wherein the mounting member is provided at a bottom of the body 11 in a widthwise middle region thereof, and is configured such that the test engine 14 is mounted in a longitudinal direction at a center line of the body 11. Both the empennage 17 and the landing gear 16 need to be designed to match the centerline of the test engine 14. When the test engine breaks down, the structure can reduce the deflection moment brought to the unmanned flight test platform, and improve the safety of testing the aircraft engine by using the unmanned aerial vehicle.
As shown in fig. 2, two running engines 12 are provided, and two running engines 12 are provided below the side wings 13 on both sides of the body 11, respectively, for example, the running engines 12 may be turbofan or turboprop engines. Compared with passenger planes or transport planes, the unmanned plane does not need to bear huge passenger cabins and cargo hold systems, and the mechanical structure is greatly simplified; and moreover, a cabin system and a control system are not required to be additionally arranged in the unmanned piloting process, so that the configuration of the airplane is further simplified. The greatly simplified structure and aircraft configuration can reduce the weight of the aircraft and also can reduce the design difficulty. Therefore, the working requirements of the unmanned aerial vehicle test platform 1 can be met by using the two running engines 12 as power sources.
As shown in FIG. 2, the mounting member includes a hanger 15, the hanger 15 being provided at the bottom of the fuselage 11 for attachment to the top of the test engine 14. Part unmanned aerial vehicle is equipped with general suspended structure in order to carry article in the 11 bottoms of fuselage, in order to reduce the repacking to the original structure of unmanned aerial vehicle platform, and 14 accessible switching suspended structure of experimental engine are connected with general suspended structure to install experimental engine 14 in the 11 bottoms of fuselage.
The structure can improve the dismounting convenience of the test engine 14, so that the test efficiency is improved, and the structure can be suitable for testing the test engines 14 of different models and has strong universality.
In some embodiments, as shown in fig. 3, the test system of the present invention further includes an accompanying flying aircraft 2, where the accompanying flying aircraft 2 is a manned aircraft, and is configured to fly with the unmanned flying test platform 1, monitor the test state of the unmanned flying test platform 1 in the air, and/or control the operation of the unmanned flying test platform 1. For example, the flying aircraft 2 may be a business aircraft or a light aircraft, which is appropriately modified.
When the preset test airspace is in a sea area, the ground control station is inconvenient to set; when the preset test airspace is in a mountain area, the signal cannot be smoothly transmitted with the ground control station 3 due to weak signal; when the preset test airspace is far away from the ground control station, the signal is difficult to transmit smoothly due to the fact that the signal receiving strength is weakened. For the above situations, the test process can be flexibly controlled and monitored by the accompanying flying aircraft 2, so that the accompanying flying aircraft 2 is independently matched with the unmanned flying test platform 1 to complete the test project.
Preferably, before the unmanned flight test platform 1 takes off, the companion aircraft 2 can take off to a preset height in advance to wait in the air, and can timely find the problems encountered by the unmanned flight test platform 1 in the take-off process and return to check in time under the condition of the problems, so that potential safety hazards are reduced. The safety of the test process can be improved by the active control function and the monitoring function of the accompanying airplane 2. Alternatively, the companion aircraft 2 may take off synchronously with the unmanned flight test platform 1 or take off at the back.
The unmanned flight test platform 1 can be provided with various sensors for detecting test state data of the flight test platform 1, the accompanying flight aircraft 2 can receive the test state data sent by the unmanned flight test platform 1 so as to allow a participant to monitor the test process on the accompanying flight aircraft 2, and in the synchronous flight process of the accompanying flight aircraft 2 along with the flight test platform 1, the participant can also visually observe the flight state of the flight test platform 1 through naked eyes so as to master the test condition at any time, so that the monitoring is easy, and emergency measures can be adopted in time when special conditions occur, so that the safety of the test process is improved, and the loss is reduced.
In some embodiments, the testing system of the present invention further comprises a ground control station 3 for monitoring the test status of the unmanned aerial vehicle test platform 1 on the ground and/or controlling the operation of the unmanned aerial vehicle test platform 1. The ground control station 3 may utilize existing flight control base stations, or may also be flexibly re-established as needed, reducing the cost of the test compared to an aerial control and monitoring approach. Moreover, the operation of a tester and the machine does not need to be participated, and the influence of the engine test on the personal safety can be avoided.
In some embodiments, the test system of the present invention includes the accompanying flying aircraft 2 and the ground control station 3, the accompanying flying aircraft 2 and the ground control station 3 independently control the operation of the unmanned flying test platform 1, and the accompanying flying aircraft 2 or the ground control station 3 independently control the operation of the unmanned flying test platform 1 at the same time.
In the embodiment, the accompanying airplane 2 and the ground control station 3 are arranged at the same time, which is equivalent to increase the redundancy of test control, so that a proper control mode can be flexibly selected according to the actual situation, and the control mode can be switched to another control mode in time under the condition that one control mode cannot be normally implemented.
For example, in a normal state, in order to reduce the operation burden of a test person in the flying companion aircraft 2, the ground control station 3 may be used to independently control the operation of the unmanned aerial vehicle test platform 1, and when the communication between the unmanned aerial vehicle test platform 1 and the ground control station 3 is not smooth or an emergency occurs during the test, the flying companion aircraft 2 may take over the control right of the flying test platform 1 at any time, and after the normal state is recovered, the control right is returned to the ground control station 3.
In some embodiments, when the preset test airspace is not more than the preset distance from the ground control station 3, normal communication can be realized between the unmanned flight test platform 1 and the ground control station 3, the ground control station 3 controls the operation of the unmanned flight test platform 1 in a normal state, and the accompanying flying aircraft 2 takes over to control the operation of the unmanned flight test platform 1 in an emergency. Therefore, the operation burden of the test personnel in the accompanying airplane 2 can be reduced, and the safety of the flight test can be improved.
When the distance between the preset test airspace and the ground control station 3 exceeds the preset distance, the problem of unsmooth communication may occur between the unmanned flight test platform 1 and the ground control station 3, the remote control difficulty is high, and the operation of the unmanned flight test platform 1 is directly controlled by the accompanying flying aircraft 2. Therefore, controllability and monitoring accuracy of the unmanned flight test platform 1 in the whole test process can be improved, and test safety is improved.
In some embodiments, the test system of the present invention further includes a companion aircraft 2 and a ground control station 3, wherein the communication between the companion aircraft 2 and the unmanned flight test platform 1, between the companion aircraft 2 and the ground control station 3, and between the unmanned flight test platform 1 and the ground control station 3 is performed via data links. The unmanned flight test platform 1 is used for directly transmitting the operation state data to the ground control station 3 and/or backing up and relaying the operation state data to the ground control station 3 through the accompanying flying aircraft 2.
Under the condition of good communication between the unmanned aerial vehicle test platform 1 and the ground control station 3, the running state data can be transmitted to the ground control station 3, so that the timeliness of the ground control station 3 for receiving the state data is improved, and the test condition is monitored in real time.
If the distance between the unmanned flight test platform 1 and the ground control station 3 is far and good communication state is difficult to realize, because the accompanying aircraft 2 is close to the unmanned flight test platform 1, the accompanying aircraft 2 receives the state data of the unmanned flight test platform 1 and forwards the state data to the ground control station 3, test data can be prevented from being lost, and the test personnel on the accompanying aircraft 2 can monitor the test condition in real time through the data, and can take emergency control measures in time when special conditions occur in the test process. The companion aircraft 2 can backup the data and transmit the data to the ground control station 3 in batch or in whole in the case of good communication. The mode of state data transmission can improve the safety of the engine test.
In some embodiments, a flight control system is provided in unmanned flight test platform 1, the flight control system including a thrust control module for adjusting the thrust of operating engine 12 to meet the test thrust requirements of test engine 14. Because the running engine 12 and the test engine 14 provide the flight thrust of the unmanned flight test platform 1 together, when the test engine 14 is tested according to the preset load spectrum, the thrust of the running engine 12 can be adjusted, so that the total thrust meets the flight requirement. For example, the thrust to operate the engine 12 is calculated from a preset load spectrum so that the total thrust remains constant.
In a specific test project, the unmanned flight test platform 1 is used for measuring flight thrust, and thrust corresponding to different rotating speeds of the test engine 14 under the condition of different altitude and speed needs to be determined, wherein the specific measuring method comprises the following steps:
1. the unmanned flight test platform 1 reaches a preset height and stably flies at a preset speed;
2. adjusting the rotating speed of the test engine 14 to a first test value, and adjusting the thrust of the test engine 14 in a matching manner so as to maintain the total thrust of the unmanned flight test platform 1 unchanged and further maintain the altitude speed of the unmanned flight test platform 1;
3. acquiring test data after the unmanned flight test platform 1 is in a stable state;
4. adjusting the rotating speed of the test engine 14 to a second test value, re-matching and adjusting the thrust of the test engine 14, and obtaining test data after the state is stable;
5. thus, the performance of the test engine 14 in the full rotating speed range is repeatedly obtained at the specified altitude speed;
6. and adjusting the height speed of the unmanned aerial vehicle test platform 1, and obtaining the performance of the test engine 14 in the full rotating speed range again.
In another specific test item, the unmanned aerial vehicle test platform 1 is used for carrying out the test of the natural icing in the air of the test engine 14, and the specific test method is as follows:
1. enabling the unmanned flight test platform 1 to fly to a preset test airspace;
2. collecting environmental icing parameters by using a sensor arranged on the unmanned flight test platform 1;
3. starting an engine test after the environmental conditions are met, and acquiring state data of a test engine 14 in the test process;
4. if the vibration of the test engine 14 reaches the limit value in the test process, automatically starting an ice falling program;
5. the unmanned flight test platform 1 keeps running under the icing condition according to the feedback of the environmental sensor until the test is finished.
In a specific embodiment, the test system of the invention comprises an unmanned flight test platform 1, a companion aircraft 2 and a ground control station, and the functions and data exchange relationship among the subsystems are shown in fig. 3.
Wherein, unmanned aerial vehicle test platform 1 includes: the flight control module is used for controlling the flight state of the unmanned flight test platform 1, wherein the flight control module comprises a thrust control module and is used for adjusting the thrust of the running engine 12 so as to meet the test thrust requirement of the test engine 14; a test engine control module for controlling operating parameters of the test engine 14; an operating engine control module for controlling operating parameters of the operating engine 12; the data acquisition and storage module is used for acquiring the engine working state data detected by each sensor and storing the data in the memory; the data sending module is used for sending the working state data outwards; the emergency protection module is used for starting safety protection when an emergency occurs in the flying process of the unmanned flying test platform 1; and the backup control module is used for switching to the backup control channel when the current control channel fails.
Further, the companion aircraft 2 includes: the operation monitoring module is used for monitoring the state data sent by the data sending module of the unmanned flight test platform 1 so as to judge whether the flight process is abnormal or not; the data storage module is used for storing the state data sent by the data sending module of the unmanned flight test platform 1; the data processing module is used for processing the received state data so as to judge the current test state; the data relay module is used for forwarding the state data sent by the data sending module of the unmanned aerial vehicle test platform 1 to the ground control station 3 through a data chain; and the remote control module is used for remotely controlling the flight state of the unmanned flight test platform 1 in the accompanying flight process.
Further, the ground control station 3 comprises an operation monitoring module for monitoring the state data sent by the data sending module of the unmanned aerial vehicle test platform 1 to judge whether the flight process is abnormal; the data storage module is used for storing the state data sent by the data sending module of the unmanned flight test platform 1 or the accompanying aircraft 2; the data processing module is used for processing the received state data so as to judge the current test state; and the remote control module is used for remotely controlling the flight state of the unmanned flight test platform 1 on the ground.
In the test process, any two of the unmanned flight test platform 1, the accompanying flying aircraft 2 and the ground control station 3 can be communicated through a data chain. In order to meet the test requirements, an airspeed calibration system, a bleed air load simulation system, an electrical load simulation system and other systems can be further arranged on the unmanned flight test platform 1 to simulate the actual aircraft operation conditions.
Secondly, the invention provides a test method of the aircraft engine flight test system based on the above embodiments, and in some embodiments, the test method includes:
101, enabling an unmanned flight test platform 1 to be in a preset test airspace;
102, controlling the unmanned aerial vehicle test platform 1 to operate to execute a preset test project; and
and 103, returning the unmanned flight test platform 1 to the running state data.
The step 101 is executed before the step 102, if the predetermined test items are all completed in the same preset test airspace, the step 101 only needs to be executed once, and if the predetermined test items are completed in different preset test airspaces, the test items need to fly to the corresponding test airspace before the test. Step 103 may be performed after each predetermined test item is performed, or may be performed in real time during the course of the test. The advantages of using the unmanned aerial vehicle test platform 1 to test an aircraft engine are already described in the test apparatus section and will not be described further herein.
In some embodiments, the assay methods of the invention further comprise:
104, flying along with the unmanned flight test platform 1 through the accompanying airplane 2, and monitoring the test state of the unmanned flight test platform 1 in the air; and/or
And 105, monitoring the test state of the unmanned aerial vehicle test platform 1 on the ground through the ground control station 3.
Wherein steps 104 and 105 can be executed synchronously with step 102, i.e. the flight status is monitored during the test. Steps 104 and 105 are executed after step 103 while monitoring by receiving status data returned by the unmanned aerial vehicle test platform 1 through the companion aircraft 2 or the ground control station 3; the order of execution of steps 104 and 103 is not limited when the flight status is directly observed by the test taker in the companion aircraft 2.
The test process is monitored by the accompanying airplane 2, and the method has the advantages that the accompanying airplane 2 can be independently matched with the unmanned flight test platform 1 to complete test items, and the method can be suitable for the condition that a ground control station is inconvenient to set or signals cannot be smoothly transmitted with the ground control station 3; and the test condition can be mastered at any time, the monitoring is easy, and emergency measures can be adopted in time when special conditions occur, so that the safety of the test process is improved, and the loss is reduced.
The advantage of monitoring the test process by means of the ground control station 3 is that the existing flight control base station can be used, or the ground control station 3 can be flexibly re-established as required, which reduces the test costs compared to the air control and monitoring approach. Moreover, the operation of a tester and the machine does not need to be participated, and the influence of the engine test on the personal safety can be avoided.
In some embodiments, the step 102 of controlling the operation of the unmanned aerial vehicle test platform 1 specifically includes:
102A, independently controlling the operation of the unmanned flight test platform 1 through the accompanying flying aircraft 2; or
And step 102B, independently controlling the operation of the unmanned aerial vehicle flight test platform 1 through the ground control station 3.
Wherein, only step 102A or 102B can be executed at the same time, and only the accompanying flying aircraft 2 or the ground control station 3 can independently control the operation of the unmanned flying test platform 1.
In the embodiment, the accompanying airplane 2 and the ground control station 3 are arranged at the same time, which is equivalent to increase the redundancy of test control, so that a proper control mode can be flexibly selected according to the actual situation, and another control mode can be timely switched to under the condition that one control mode cannot be normally implemented.
In some embodiments, the test system includes a flight accompanying aircraft 2 and a ground control station 3, and the step 102 of controlling the operation of the unmanned aerial vehicle test platform 1 specifically includes:
step 201, judging whether a preset test airspace exceeds a preset distance from the ground control station 3, if not, executing step 202 in a normal state, and executing step 203 in an emergency; if yes, go to step 203;
step 202, controlling the operation of the unmanned aerial vehicle test platform 1 through the ground control station 3,
and step 203, controlling the operation of the unmanned flight test platform 1 through the accompanying airplane 2.
In the embodiment, when the preset test airspace is close to the ground control station 3, the control mode can reduce the operation burden of the test personnel in the accompanying airplane 2 and improve the safety of the flight test; when the preset test airspace is far away from the ground control station 3, the controllability and the monitoring accuracy of the unmanned flight test platform 1 in the whole test process can be improved by the control mode, and the test safety is improved.
In some embodiments, the test system includes a companion aircraft 2 and a ground control station 3, and the step 103 of returning the unmanned aerial vehicle test platform 1 to the operation state data specifically includes:
the unmanned flight test platform 1 directly transmits the operation state data to the ground control station 3, or the operation state data is backed up by the accompanying flying aircraft 2 and transmitted to the ground control station 3 in a relay manner.
In this embodiment, the running state data is transmitted to the ground control station 3 in a state where the unmanned aerial vehicle test platform 1 and the ground control station 3 communicate well, so that the timeliness of the ground control station 3 for receiving the state data can be improved, and the test condition can be monitored in real time. Under the unsmooth state of unmanned flight test platform 1 and ground control station 3 communication, the mode of forwardding data and backing up can prevent that the test data from losing, and the reference personnel that accompanies on the flight aircraft 2 accessible data real time monitoring test condition moreover, can in time take emergency control measure when special circumstances takes place in the testing process, improve the experimental security of engine.
In some embodiments, the unmanned aerial vehicle test platform 1 is provided with a thrust control module, and the step 102 of controlling the operation of the unmanned aerial vehicle test platform 1 to execute the predetermined test items specifically includes:
the thrust of the operating engine 12 is adjusted by the thrust control module to meet the test thrust requirements of the test engine 14.
This embodiment can both test the test engine 14 according to a preset load spectrum and meet the total thrust requirements of the flight.
In some embodiments, before the unmanned aerial vehicle test platform 1 is in the preset test airspace in step 101, the test method of the present invention further includes:
and step 100, taking off the companion flying aircraft 2 to wait for the unmanned flying test platform 1 to take off in the air.
In the embodiment, the accompanying flying aircraft 2 takes off to the preset height in advance and waits in the air, so that the problems of the unmanned flight test platform 1 in the taking-off process can be found in time, the unmanned flight test platform can return to check in time under the condition of problems, and potential safety hazards are reduced.
In some embodiments, before the unmanned aerial vehicle test platform 1 is in the preset test airspace in step 101, the test method of the present invention further includes:
step 100', a flight test program on the unmanned flight test platform 1 is preset, so that the unmanned flight test platform 1 automatically completes a preset test project.
The execution sequence of the steps 100' and 100 is not limited, and all flight test programs are set in advance, so that the preset test items can be automatically completed, and the test efficiency and accuracy are improved.
An example of the aerial testing of a test engine 14 using the test system of the present invention is given below in one specific embodiment.
1. The test engine 14 is arranged below the fuselage of the unmanned flight test platform 1 through a hanging structure 15, for example, the test engine can be arranged on a universal hanging hook below the fuselage through a switching hanging;
2. a flight test program on the unmanned flight test platform 1 is preset so that a flight control system in the unmanned flight test platform 1 can automatically control the test process;
3. the accompanying flying aircraft 2 takes off in advance and waits in the air;
4. the unmanned flight test platform 1 starts a test engine 14 and runs the engine 12;
5. enabling the unmanned flight test platform 1 to automatically take off and climb, flying to a preset test airspace, executing a preset test subject, relaying state data returned by the unmanned flight test platform 1 to the accompanying flying aircraft 2 for backup, and forwarding the state data to the ground control station 3 by the accompanying flying aircraft 2; or the state data returned by the unmanned flight test platform 1 can also be directly sent to the ground control station 3;
6. in the test process, the unmanned flight test platform 1 automatically adjusts the thrust of the running engine 12 through an automatic flight control system and a thrust management system so as to match the power adjustment and flight state requirements of the test engine 14;
7. in the test process, the accompanying flying aircraft 2 and/or the ground control station 3 monitor the operation parameters and the test engine parameters of the unmanned flight test platform 1 in the whole process, and in an emergency, the ground control station 3 or the accompanying flying aircraft 2 can remotely take over control;
8. after the test is finished, the accompanying airplane 2 or the ground control station 3 sends a return command, the unmanned flight test platform 1 returns, and the accompanying airplane 2 returns.
Wherein, the steps 1-5 and 8 are executed in sequence, and the steps 6 and 7 are specific control and monitoring methods in the test process. In the test process, the accompanying flying aircraft 2 and the ground control station 3 can be used simultaneously or independently as required. If the conditions allow, the unmanned flight test platform 1 can automatically complete the test task in the whole process under the pre-programming and ground control.
The aircraft engine flight test system and the test method provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to aid in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (14)
1. The aircraft engine flight test system is characterized by comprising an unmanned flight test platform (1), wherein the unmanned flight test platform (1) comprises:
the test device comprises a machine body (11), wherein the outer bottom of the machine body (11) is provided with a mounting component for mounting a test engine (14); and
an operating engine (12) provided at a side of the body (11);
the aircraft engine flight test system further comprises: the flight accompanying aircraft comprises a flight accompanying aircraft (2) and a ground control station (3), wherein the ground control station (3) is used for monitoring the test state of the unmanned flight test platform (1) on the ground and/or controlling the operation of the unmanned flight test platform (1); the flight accompanying aircraft (2) and the ground control station (3) independently control the operation of the unmanned flight test platform (1), and the flight accompanying aircraft (2) or the ground control station (3) independently control the operation of the unmanned flight test platform (1) at the same time;
when a preset test space is not more than a preset distance from the ground control station (3), the ground control station (3) independently controls the operation of the unmanned flight test platform (1) in a normal state, the communication between the unmanned flight test platform (1) and the ground control station (3) is not smooth, or the test process is in an emergency, the accompanying airplane (2) takes over to control the operation of the unmanned flight test platform (1), and the control right returns to the ground control station (3) after the test is normal; and/or
When the distance between a preset test airspace and the ground control station (3) exceeds the preset distance, the accompanying flying aircraft (2) controls the operation of the unmanned flying test platform (1).
2. The aircraft engine flight test system according to claim 1, wherein the mounting member is provided in a transversely intermediate region of the fuselage (11) and is configured to mount the test engine (14) longitudinally at a centerline of the fuselage (11).
3. An aircraft engine flight test system according to claim 1, characterised in that the mounting means comprises a hanger structure (15), the hanger structure (15) being for connection with the top of the test engine (14).
4. An aircraft engine flight test system according to claim 1, characterised in that there are two of the running engines (12), the two running engines (12) being respectively provided below the side wings (13) on both sides of the fuselage (11).
5. The aircraft engine flight test system according to claim 1, further comprising a flying companion aircraft (2), wherein the flying companion aircraft (2) is a manned aircraft and is used for flying with the unmanned flight test platform (1), monitoring the test state of the unmanned flight test platform (1) in the air and/or controlling the operation of the unmanned flight test platform (1).
6. The aircraft engine flight test system according to claim 1, further comprising a companion aircraft (2) and a ground control station (3), wherein,
the accompanying flying aircraft (2) and the unmanned flying test platform (1), the accompanying flying aircraft (2) and the ground control station (3) and the unmanned flying test platform (1) and the ground control station (3) are communicated through data chains;
the unmanned flight test platform (1) is used for directly transmitting the operation state data to the ground control station (3) and/or backing up the operation state data through the accompanying flying aircraft (2) and transmitting the operation state data to the ground control station (3) in a relay mode.
7. The aircraft engine flight test system according to claim 1, characterized in that a flight control system is provided in the unmanned flight test platform (1), the flight control system comprising a thrust control module for adjusting the thrust of the running engine (12) to meet the test thrust requirement of the test engine (14).
8. A test method based on the aircraft engine flight test system of any one of claims 1 to 7 is characterized by comprising the following steps:
enabling the unmanned flight test platform (1) to be in a preset test airspace;
controlling the unmanned aerial vehicle test platform (1) to operate to execute a predetermined test project; and
returning the unmanned aerial vehicle test platform (1) to the operating state data;
the method comprises the following steps of controlling the unmanned flight test platform (1) to run:
judging whether the preset test airspace exceeds a preset distance from the ground control station (3), if not, independently controlling the operation of the unmanned flight test platform (1) through the ground control station (3) in a normal state, and taking over the operation of the unmanned flight test platform (1) through the accompanying flying aircraft (2) to control the operation of the unmanned flight test platform (1) under the condition that the communication between the unmanned flight test platform (1) and the ground control station (3) is not smooth or the emergency occurs in the test process, and returning the control right to the ground control station (3) after the test is normal; if the number of the unmanned aerial vehicle exceeds the preset value, the operation of the unmanned aerial vehicle test platform (1) is controlled by the accompanying airplane (2).
9. The assay of claim 8, further comprising:
the accompanying airplane (2) flies along with the unmanned flight test platform (1), and the test state of the unmanned flight test platform (1) is monitored in the air; and/or
And monitoring the test state of the unmanned flight test platform (1) on the ground through a ground control station (3).
10. The test method according to claim 8, characterized in that the step of controlling the operation of the unmanned aerial vehicle test platform (1) comprises in particular:
the operation of the unmanned flight test platform (1) is controlled independently through a flying accompanying airplane (2); or
The operation of the unmanned aerial vehicle flight test platform (1) is independently controlled through a ground control station (3).
11. Test method according to claim 8, characterized in that the step of returning the unmanned aerial vehicle test platform (1) with operating state data comprises in particular:
enabling the unmanned flight test platform (1) to directly transmit the operation state data to the ground control station (3), or enabling the operation state data to be backed up through the accompanying flying aircraft (2) and transmitted to the ground control station (3) in a relay mode.
12. The test method according to claim 8, wherein a flight control system is arranged in the unmanned aerial vehicle test platform (1), the flight control system comprises a thrust control module, and the step of controlling the unmanned aerial vehicle test platform (1) to operate to execute the predetermined test item specifically comprises:
adjusting, by the thrust control module, a thrust of the operating engine (12) to meet a test thrust requirement of the test engine (14).
13. The test method according to claim 8, characterized in that before bringing the unmanned aerial vehicle test platform (1) in a preset test airspace, it further comprises:
taking off the accompanying airplane (2) to wait for the unmanned flight test platform (1) to take off in the air.
14. The test method according to claim 8, characterized in that before bringing the unmanned aerial vehicle test platform (1) in a preset test airspace, it further comprises:
and presetting a flight test program on the unmanned flight test platform (1) so as to enable the unmanned flight test platform (1) to automatically complete the preset test items.
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| CN112947378A (en) * | 2021-02-24 | 2021-06-11 | 西安交通大学 | Turbojet engine fault-tolerant test system and method based on unmanned aerial vehicle carrying platform |
| CN113060291A (en) * | 2021-05-25 | 2021-07-02 | 复旦大学 | Engine mounting bracket for fixed-wing unmanned aerial vehicle and fixed-wing unmanned aerial vehicle |
| CN113310701B (en) * | 2021-06-15 | 2022-06-10 | 中国人民解放军93208部队 | Complete machine tester for mechanical system of military turbofan engine |
| CN113615672A (en) * | 2021-08-30 | 2021-11-09 | 山东元一动力科技有限公司 | Jet-propelled plant protection atomizing machine |
| CN114001964B (en) * | 2021-11-02 | 2024-02-02 | 中国航发沈阳发动机研究所 | Flight table with large-span S-bend air inlet and exhaust system |
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| US8897931B2 (en) * | 2011-08-02 | 2014-11-25 | The Boeing Company | Flight interpreter for captive carry unmanned aircraft systems demonstration |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN103728140B (en) * | 2013-12-04 | 2017-01-04 | 中国飞行试验研究院 | A kind of small-size turbojet engine flight test pod |
| FR3028067B1 (en) * | 2014-11-05 | 2016-12-30 | Snecma | VALIDATION TOOL FOR A SYSTEM FOR MONITORING AN AIRCRAFT ENGINE |
| CN104536455B (en) * | 2014-12-15 | 2017-02-01 | 中国航空工业经济技术研究院 | Flight control method of unmanned general aircraft with flight experience function |
| GB2551112B (en) * | 2016-05-25 | 2020-04-15 | Ge Aviat Systems Ltd | Aircraft component monitoring system |
| CN108918152B (en) * | 2018-05-18 | 2020-10-23 | 中国航发湖南动力机械研究所 | Aeroengine test device |
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